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At a glance
R-36 (missile)larger figure on 4 of 4
Shaurya (missile)larger figure on 0 of 4
Counts only measures both sources give with the same scope. A larger figure is not a better system.
Measured figures
Length
Single sourceR-36-O
Single sourceConfiguration
| Specification | R-36 (missile) | Shaurya (missile) |
|---|---|---|
| Type | Intercontinental ballistic missile[source] | Short-range ballistic missile[source] |
| Place of origin | Soviet Union[source] | India[source] |
| In service | 1966–1979 (original variant) 1988–present (R-36M2 Voevoda variant)[source] | — |
| Used by | Russian Strategic Rocket Forces[source] | Strategic Forces Command[source] |
18,900 mm (740 in) - (R-36-O) 32,200 mm (1,270 in)[source]
Length
Single source10 m (33 ft )[source]
Maximum; 2.55 km/s
Single sourceMaximum; Mach 7.5 (
Single sourceMach 7.5 (9,190 km/h; 5,710 mph; 2.55 km/s)[source]
Warhead weight
Single source200–1,000 kilograms (440–2,200 lb)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Designed | From 1962[source] | — |
|---|
| Manufacturer | Factory: Yuzhny Machine-Building Plant Developer: Yuzhnoye Design Office[source] | Bharat Dynamics Limited[source] |
|---|
| Unit cost | $7,000,000[source] | — |
|---|
| Warhead | Depending on variant (see variants). Newest (R-36M2), 10 × 550–750 kiloton MIRV warheads with a large amount of decoys and other penetration aids . Originally (R-36), 1 × 8–20 megaton warhead.[source] | Conventional and strategic nuclear weapon[source] |
|---|
| Engine | Two or three (R-36MUTTKH and R-36M2) liquid fueled rocket stages First Stage: 1x RD-251 (R-36) 1x RD-251P (R-36P) 1x RD-251M (R-36-O) 1x RD-264 (R-36M) 1x RD-264 (R-36MUTTKh and R-36M2) Second Stage: 1x RD-252 (R-36) 1x RD-252 (R-36P) 1x RD-0228 (R-36M) 1x RD-0255 (R-36MUTTKh) 1x RD-0255 (R-36M2) Third Stage: 1x RD-864 (R-36MUTTKh) 1x RD-869 (R-36M2)[source] | Two-stage solid rocket motor[source] |
|---|
| Propellant | N 2 O 4 / UDMH[source] | Solid fuel[source] |
|---|
| Guidance system | Inertial, autonomous[source] | RLG - INS and accelerometer[source] |
|---|
| Accuracy | 220–1,300 m CEP[source] | 20 m to 30 m CEP[source] |
|---|
| Launch platform | Silo[source] | Canisterised transporter erector launcher or underground silo[source] |
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| Designer | — | Research Centre Imarat[source] |
|---|
| Produced | — | 2011–present[source] |
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| Flight altitude | — | 50 km (31 mi)[source] |
|---|
| Reported operators | — |
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